Jet powered vtol aircraft



1964 T. 0 RYAN ETAL 3,159,360

' JET POWERED VTOL AIRCRAFT Filed Jan. 20, 1964 e Sheets-Sheet 1 INVENTORS TUBAL CLAUDE RYAN PETER F. GIRARD Dec. 1, 1964 -T. c. RYAN ETAL JET POWERED V'IOL AIRCRAFT 6 Sheets-Sheet 2 Filed Jan. 20, 1964 INVENTORS TUBAL CLAUDE RYAN PETER F. GIRARD JET POWERED VTOL AIRCRAFT Dec. 1, 1964 6 Sheets-Sheet 3 Filed Jan. 20, 1964 N .9 LL

r r Q i i Q J/ g 1- E g% s o o r S! INVENTORS A TUBAL CLAUDE RYAN PETER F. GIRARD I BY g g jaws-x & 142m Dec. 1, 1964 T. c. RYAN ETAL JET POWERED VTOL AIRCRAFT 6 Sheets-Shet 4 Filed Jan. 20, 1964 1NVENTORS TUBA'L CLAUDE RYAN PETER F. GIRARD &

Dec. 1, 1964 T. c. RYAN ETAL 3,159,360

JET POWERED VTOL AIRCRAFT Filed Jan. 20, 1964 6 Sheets-Sheet 5 STOPP|NG SIGNAL WING LOCKING SIGNAL TO FLUID PRESSURE I SOURCE FORWARD FLIGHT INTERLOCKING INVENTORS TUBAL CLAUDE RYAN PETER F. GIRARD Fig. IO 48 BY 16:14:36 & 161.01:

Dec. 1, 1964 T- c. RYAN ETAL 3,159,350

JET POWERED VTOL AIRCRAFT Filed Jan. 20, 1964 6 Sheets-Sheet 6 TO FLUID PRESSURE Fig. I3 I16 I l INVENTORS TUBAL CLAUDE RYAN PETER F. GIRARD w I [Q4 56 jcncnc & 54w

United States Patent M 3,159,369 JET IUWERED V'IUIJ AIRERAFT Tubal Claude Ryan, San Diego, and leter F. Girard, La Mesa, Qaiiii, assignors to The Ryan Aeronautical Co, San Eicgo, Calif.

Filed .Ian. 2%, 19nd, Ser. No. 333,947 7 Claims. (El. 244-7) The present invention relates to aircraft and more particularly to a jet powered VTGL aircraft.

Aircraft having vertical take-off and landing capability are powered in various ways, such as by separate engines for lift and propulsion, the lift engines being inoperable in high speed flight. Other types use defiected thrust from primary propulsion jet engines, involving deflectors or large movable nozzles which are subjected to high temperature gas flow. Helicopters have great maneuverability inhovering and low speed flight, but are limited in forwardspeed unless the rotor is made retractable bysorne complex means, and fixed wings used for lift.

The primary object of this invention is to provide an aircraft which can take off and land vertically, or with a very short run, hover, move in any direction at low speed, yet is capable of supersonic flight, with smooth and fully controlled transition between vertical and horizontal flight.

Another object of this invention is to provide an aircraft having a wing which is fixed for high speed flight, but is rotated by the primary propulsion jet engine during low speed flight and transition and has movable tip portions which act as lifting rotor elements when the wing is rotating.

Another object of this invention is to provide an aircraft wherein the wing propulsion means is not subjected to the high temperature of jet engine exhaust gases, so simplifying construction.

Another object of this invention is to provide an aircraft which is very stable in all phases of flight and has a wide range of center of gravity location under all flight conditions.

Still another object of this invention is to provide an a rcraft wherein the wing can auto-rotate to provide added lift for a safe landing in the event of engine failure.

A further object of this invention is to provide an air craft wherein the control systems for vertical and horizontal flight are interconnected, the same pilot operated controls being used, without change over, through all phases of flight and being the standard and instinctive controls of more conventional aircraft.

In the drawings:

FIGURE 1 is a side elevation viewof the aircraft;

FIGURE 2 is a top plan view thereof;

FIGURE 3 is an enlarged side elevation view of the propulsion system, with portions cut away;

FIGURE 4 is an enlarged sectional view taken on line 44 of FIGURE 3; V

FIGURE 5 is a sectional view taken on line 55 of FIGURE 3;

FIGURE 6 is a sectional view taken on line 5-6 of FIGURE 3;

FIGURE 7 is an enlarged fragmentary sectional view taken on line 77 of FIGURE 3;

FIGURE 8 is an enlarged top plan view of the wing, I

with portions cut away;

, FIGURE 9 is an enlarged fragmentary sectionfl View taken on line 9 of FIGURE 8; 7

FIGURE 10 is a diagrammatic perspective view of the basic control system;

FIGURE 11 is a diagrammatic view of the thrust control valve system;

FIGURE 12 is a diagrammatic view of the yaw control system; and

iliih ifih Fatented Dec. 1, 1964 FIGURE 13 is a top plan view of the pitch control means for the wing rotor portions.

Similar characters of reference indicate similar or identical elements and portions throughout the specification and throughout the views of the drawings.

Basic A ircraft The aircraft has a fuselage Zll, designed to suit the particular purpose of the aircraft, with a large upright pylon 22 substantially at the center of gravity position.

at any position being a substantially lenticular airfoil.

The precise aerodynamic contours of the wing will depend on the intended range of performance.

At the center of the wing 24 is a hub as freely rotatably mounted on a bearing 38 which is carried by support frames as, as in FIGURE 3, the frames being secured in a suitable manner to the main fuselage structure, not shown. The axis of bearing 38 is generally perpendicular to the longitudinal axis of the aircraft and slightly aft of the normal center of gravity position for stability reasons, although a slight inclination of the axis is indicated to give the wing a positive angle of incidence in fixed position.

At the rear of fuselage 2h is a tail assembly comprising a vertical fixed fin 42 having a movable rudder 44, and a horizontal stabilizer or tailplane 46 fixed to the top of said fin. The tailplane 4-6 is fitted with movable elevons 48 which serve as elevators and ailerons for pitch and roll control, as hereinafter described. Other tail arrangements may be used, but it is desirable to keep the tailplane high and clear of the downwash from the wing.

Landing gear, indicated in broken line in FIGURE 1, may be arranged to suit the particular aircraft.

Wing Assembly The specific structure of the wing may vary, a typical arrangement being illustrated in FIGURE 8. The center section 26 contains a ring member 5%, from which hub 36 is coaxially supported by arms 52, said ring member being connected to the center section structure through ribs 5 which form the airfoil shape. The tip portions 32 and 3d are carried by radially extending hinge shafts 56 journalled in bearings 58 in the ring member Eli and the outer ends of center section 26. Tip portion 34) is carried by a hollow hinge shaft to similarly supported in bearings 58. At the outer end of tip portion 3%) is a tip. jet unit 62 having a nozzle sa exhausting in the plane of the wing and generally perpendicular to the axis of said tip portion. shaft till by a duct 66 extending axially through the tip portion.

Diametrioally opposite tip portion Tall is a boom 6? extending radially from center section 26, symmetrically between tip portions 32 and 34. At the outer end of boom 6?) is a tip jet unit '73 having a nozzle 72 exhausting in the plane of the wingand perpendicular to the boom. Both tip jet units are at the same distance from the axis of rotation of the wing and thrust in opposite directions to apply rotation to the wing. By using tip jet propulsion, the need for anti-torque means is eliminated. A duct 74 extends from tip jet unit 70 to a plenum chamber 7'3 sur rounding hub 36, said plenum chamber also being connected to hollow hinge shaft as. The plenum chamber 76 has a downwardly projecting cylindrical throat 73 coaxial with hub 36. v

The diametrically opposed arrangement of the tip jet Tip jet unit 62 is coupled to the hollow hinge V j haust.

'in which the valve is streamlinedto the exhaust said valve having an actuating arm 126. I A' rotor control'valve 123 is similarly mounted in rotor units minimizes frontal area and drag when the wing is in fixed position in forward flight. Each tip portion could be fitted with a tip jet unit, but those on the laterally disposed tips of the stationary wing would cause excessive drag and be aerodynamically undesirable in high speed flight. The boom 68 is streamlined in cross section in the direction of rotation and is designed so that the drag of the boom is equal to the drag of the thickened parts of tip portion 30 and the associated arm 28 to accommodate duct 66. Aerodynamic balancecf thawing is further assisted by a floating flap 8d pivotally attached to the trailing edge of boom 68 to adjust itself to the direction of airflow over the boom and nullify lift efiect of the boom during wing rotation. 'Flap tlllmay be centered by light springs 82,*as in FIGURE 4, to prevent drooping in forwardflight.

the tip portion and comprising a small panel mounted on a hinge 86 to swing upwardly and forwardly, relative to the fixed position of the wing, as in FIGURE 9. Each drag brake 84is operated by a suitable actuator 88 controlled by a valve $9 which is connected to pressure lines 206 and 298, the purpose being described hereinafter in the operation of the aircrafit.

Propulsion System The sole source of propulsion for the aircraft is a high ratio bypass turbojet engine 9%, also known as a turbofan engine and being in common use in aircraft. In this type of engine a portion of the incoming air is bypassed around the turbojet itself and is propelled by a fan driven by the turbojet. .As shown somewhat diagrammatically in FIG- URES Sand 6, the turbine 92 is coupled to a fan 94 which runs in a bypass air duct annulus 96 surrounding and ,7 concentric with the turbine and extended axially by a cylindrical shroud 97. The usual high velocity, high temperature column of hot gases exhausts from the turbine 92, while the fan provides an annulus or relatively cool air which greatly addsto the total mass flow of the exfrom the top of the fuselage forward of pylon 22. The

' secondary intake opening is fitted with a plurality of doors 1&2 conforming to the fuselage contours when closed and being hinged to swing downwardly into the duct 1%, as

indicated in FIGURE 7. Doors 162 are biased to the closed position by spring elements 164 of any suitable type and will beheld closed by pressure in duct 1th) in excess of the external pressure over the doors. However, if the engine becomes starved of air, as in low speed flight when the ram efiect in the intakes98 is low, the interior reduction in pressure will causethe-doors to open and admit additional air. the downwash from wing 24, which will normally be re- The doors will also be opened by tating at the low speeds where the flow through intakes 98 may be inadequate. Secondary air flowcontrol is thus automatic and need not concern the pilot. Y The engineQl exhausts into a distributor chamber 1%, from which a rotor duct 1% extends'upwardly, and is coupled to plenum chamber throat 73 by a rotary seal 7 119 of suitable typej Extending from the rear of disitributor chamber 1% is a tailpipe 112, ending'in a propulsion nozile 1.14 below the fin 42. Tailpipe 112 has a The entire wing is, of course, balanced for smooth rotation. In the upper surface of each tip portion fr2 and 34 is a drag brake 34 extending radially on position of the aircraft to avoid a pitching action;

' gases during transition operations and control changes,

The enginefib is-provided with air intakes d3 from the I sides of the fuselage 21 and a secondary intake duct 1% I (all and are pivotally connected by tie rods 174 to the p pair of opposed lateral outlets 116 in which are pivotally -mounted; a'pair of yaw'control valves 11% having actuating arms 12%,- said valves-being aerodynamically balanced so that'pressure in the tailpipe holds the valves closed. I In the'tailpipe 112 aft of lateral outlets 116 is a thrust control valve 122 pivotally mounted'to swing between a closed position blocking the tailpipe and an open position gas flow,

inclined in any direction.

in the return ducts 2134 forward of stub ducts'136 are outlet valves 142 hinged to swing between positions blocking the return duct and positions streamlined to the flow therein. The outlet valves 142 have actuating arms 144 and are coupled in any suitable manner to operate simultaneously, said valves also being connected to rotor valve 128 by a link 14-6 to open and close in unison therewith.

The outlet valves 14?, are operated by an actuator 1 48 and thrust control valve 122 is operated by an actuator 1553, the actuators being indicated as fluid jacks for simplicity. To ensure proper control of the engine exhaust the thrust control valve 122 must open before the rotor valve 128 and outlet valves 14-2 close, a lead of about .30 degrees being desirable.

7 Similarly, valve 122 must close after valves 12% and 142 open, with a lag of about 30 degrees. This can be accompilshed in various ways by timing the actuators 148 and 150. A typical arrangement is illustrated in FIGURE-11, in which actuator 148 is controlled by a valve 152 and actuator is controlled by a valve 154. A pilot operated thrust control handle 156 is coupled by a rod 158 to both valves,'the rod'being slidable through the ends of the valve control arms 16% and 162. Rod 158 has fixed stops 164 and 166 which engage arms 16% and 162 at dilferent times-as the rod is moved, and springs 168 and170 are fitted on the rod to engage the arms in opposite directions, so allowing over travel of the rod in a particular direction relative to each valvel Thislost motion type of linkage for timed control action of valves is well known in various forms.

, Flight Control System The complete fiightcontrol system is illustrated'in FIG- URES 10, 12 and 131 The wing tip portions 30, 32 and 3d are pivotal on their respectivehinge shafts and are thus variable in .pitch relative to the center section 26.

Pitch control arms 172 extend from hinge shafts 56 and rotating ring'flidof a' swash plate 173, which can be that of conventionalhelicopter rotor and is well known in structure and operation. The non-rotating control ring rss of swash plate 178 has a. roll control arm 1S2 extending laterallyfrom one side thereof, and a hinge fitting 13d below the-ring diametrically opposite said arm,-

while projecting forwardly from' the control ring is a pitch control arm 136. A jack 188 is connectedto roll control am! 182 to provide up and down motion, a.

jack 1% being similarly connected to hinge fitting .184 and a further jack 192 to pitch control arm 1%. Jacks 188, 1% and-192 are provided respectively with proportional controlvalves 194i, 1% and 198, which have All of the jacks are control rods-2%, 282 and 264. coupled to pressure lines 2% and 208 from a fluid pres sure source, not shown, with a cut-off valve 210 installed I .between the pressure source and jacks llfitl-and 1%.. Thus 7 these latter two jacks can be shutoff, leavingjack 188 'stillioperative. A- phase, control jack'212; is attached to the outer end of roll control arm 132 to rotate the .control' ring 189 through a predetermined angle about the axisot rotation of ring 176. Jack 212 is coupled to,

7 Forward of the stub ducts 136 the return ducts are turned downwardly andend in lift nozzles 149, which are positioned substantially at the longitudinal C.G.

This arrangement is basically 23 the pressure lines 206 and 2&8 through a reversible control valve 214.

A pilot operated collective pitch control are iscoupled to a rocker shaft 218 on which is a bell crank 220, one arm of the bell crank being connected by a link 222 to a pivoted arm 224. At the pivot of arm 224 is a generally H-shaped spider member 226 pivotal at its center on an axis perpendicular to the pivotal axis of said arm, said spider member having arms 228 at opposite ends thereof, which are connected to valve control rods 2% and 292. The other arm of bell crank 220 carries a secondary bell crank 230, one arm of which is coupled to valve control rod 204, the other arm of bell crank 23% being linked to the lower end of auniversally mounted control stick 232 which operates the manner of a conventional aircraft control stick. -When collective pitch control 216 is moved, bell crank 22% causes arm 224 to swing together with spider member 226, so movingooth valve control rods 2% and 292. At the same time, secondary bell crank 230 is carried by the bell crank 220 and moves control rod 204. Thus allthree jacks 188, 190 and .192 are operated simultaneously to raise or lower swash plate 178 and apply a collective pitch change to all three tip portions 30, 32 and 34-.

Control stick 232 has lateral arms 234 whichare coupled'by cables 236 to spider arms 228, so that side-to-side rocking motion of the control stick causes corresponding rocking of spider member 226. This moves control rods 2% and 2 32 in opposite directions, causing jacks 188 and 19%) to incline swash plate 178 laterally and apply a rolling action to the cyclic pitch motion. Fore and aft motion of control stick 232 swings secondary bell crank 2353, operating jack 192 and applying a pitch control action to the cyclic pitch motion. The cyclic pitch action of a rotor is well. known and need not be described in detail.

The lateralarms 234 of control stick 232 are connected to control valves 238 and 24-8 of jacks 242 and 244, which actuate the elevons 48. Through secondary bell crank 23s the control stick is also coupled to a connecting bar 246 between the control valves 233 and 240. It will be evident that fore and aft motion of the control stick will provide collective up and down motion of elevons 48 in the manner of elevators, while lateral motion of the stick willprovide difierential action in the manner of ailerons. Thus the vertical and horizontal flight controls are interconnected and operated by common control means.

Yaw control is provided by a conventional rudder bar 248, is in FIGURE 12, or by a pair of pedals, the rudder bar being connected by rods s to the actuating arms 12%) of yaw control valves 118. Rods 259 are slidable through arms 12d and each have a stop 252 on one side of the arm with a spring 254 on the other side,-allowing each valve to operate independently with one opening while the other remains closed. Rods 25% extend to the rudder 44 which is operated in conjunction with the yaw control valves 118 to avoid separate controls. The neutral position of the mechanism is indicated full line in FIGURE 12, with an ofiset position for a turn to the right indicated in broken line.

The control system asillustrated is merely a simplified example of a working system and is in no way limited to the specific mechanisms or actuators shown.

Wing 24 is held in the fixed position by a latch 25s operated by an actuator 258 in the pylon 22, said latch engaging in a socket member 260 in the arm 28 carryingtip portion 3t as in FIGURE 10. Actuator 258 is connected through a latching valve 262 to the pressure supply lines 2% and 208, the valve being controlled by a suitable signal, either initiated by the pilot or. by automatic means whenthe wing stops rotating.

Operation For vertical take-oil control handle 156 is set to open rotor control valve 128 and outlet valves 142, with thrust control valve 122 closed, as indicated in broken line positions in FIGURES 3 and 11. The exhaust gases from engine 93 are then diverted into the rotor duct N8 and I return ducts 134. Within the distributor chamber the hot engine exhaust gases and cool bypass air mix to some extent, so that the resultant exhaust is cooled before reaching the wing plenum chamber 76. The hot exhaust gases are carried beyond rotor duct 108 by the shroud 97 and flow back through return ducts 1.34, mixed together with cool bypass air,'to mix further through baffles 138 withthe bypass air flowing to the rotor duct. The degree of mixing can be controlled by the particular design of the distributor chamber 166, the mixing baflles 13 8, and other factors. If-necessary, vanes or other devices can be used to increase mixing. In any event, the gases directed to the wing are considerably cooler than the direct turbine efllux and the materials used in the wing ducts and tip jets need'not have the high heat resistance of-the-tailpipe and engine portions. The gases are fed from plenum chamber 76 throughlducts 66 and '74 to the tip jet units 62 and 7d, the resultant thrust position indicated in broken line in FIGURE 13. In this position the motions of the swash plate 178 are applied 'to the. arms 172 to control the tip portions at the proper time during rotation, as in conventional helicopter practice. Control stick 232 is used to control the aircraft by cyclic pitch changes inthe manner of a helicopter, yaw or directional control being obtained by the selective opening of valves lid through rudder bar 248 to provide lateral thrust. A portion of the exhaust gases flowing back through return ducts 134 is exhausted downwardly from lift nozzles 14%, so adding to the overall lift of the aircraft. If the engine does not receive sutficient air through intakes 98, the doors 102 will openautomatically and admit additional air from the downwash of the-wing.

For transition to forward flight, control handle 156 is movedto beginopening thrust control valve 122, so that exhaust gases-are expelled from propulsion nozzle 114 and the aircraft begins to move forward. At the same time the gas flow to the tip jets s2 and 70 is reduced and wing rotation begins to slow down. As forward speed increases the aerodynamic-lift of the wing compensates for. the reduction in rotor lift, control being maintained constantly through cyclic and collective pitch control until the aerodynamic surfaces become eifective. The elevons l8 and rudder t are operable at all times with the wingand lateral thrust control means, transition being smooth and positive.

Valves 128 and 142 are now closed, with thrust control valve 122 fully open to apply all engine thrust to forward propulsion, as indicated in the full line positions extended and, with no power and the added drag, the I wing is rapidly stopped. Since the drag brakes 84 are radiallymounted on tip portions 32 andsd, the airflow over the wing will tend to streamline the drag brakes to the flow with a balancing action. This balanced drag automatically aligns the tip portion 3tluforwardly over the pylon 22, 50 that latch 2% can .be engaged to lock the wing in place, after which drag brakes 84 are retracted.

Phase control jack 212 is then operated to return the control ring loll to the forward flight position indicated in full line in' FIGURE 13 and as shown in FIGURE 10,

at the same time closing cut-off valve 210 and disabling v jacks 196 and 192. It will be evident that in this position, the arms 17?. from laterally disposed tip portions 32'and lateral motion of control stick 232 will actuate this single jack and raise and lower one side of swash plate 178, pivoting about hinge fitting 184. The end connections of all jacks will be pivotally capable of handling all the necessary motions, suitable fittings being readily available. This particular swash plate motion will cause the tip portions '32 and 34 to move in opposite directions in the manner of ailerons and in conjunction with elevons 48.

Rudder 44 and valves 118 operate in unison at all times, thus the entire control system is continuously operable by. the same pilots controls and by the same 'actions' through all phases of iiightyrnaking the aircraft transition process. The wing is unlatched, then control handle 156 is movedto direct the engine exhaust gases to the tip'jet 62 and '70, while blocking off propulsion nozzle 114, so that forward speed is reduced. Control ring 189 is moved to the vertical flight position .by phase control jack 232 and the aircraft is flown in the manner of a helicopter to the required landing area. i

' The combined wing and rotor is very efiicient over an extremely wide speed range. The wing can be of small area compared to those of conventional aircraft, since the wing is used in fixed position only in high speed flight when a high'wing loading is normal in jet aircraft.

,In rotating operation the large effective disc area has a low disc loading for vertical takeoff and landing, the large tip portions providing a considerable rotor area. The opposed arrangement of the tip jets greatly reduces drag at high speed. The wing is used in its entirety in both vertical md horizontal flight and at all speeds, without the need for retractable structures or changes inconfiguration, andthe structure is adaptable to aircraft of various performance characteristics.

'It is understood that minor variation from the form of the'invention disclosed herein may be made without departure from the spirit and scope of the invention, and

pivotally mounted on substantially radial axes for 1 inclination relative to the chord plane of the wing;

control means operatively connected to said tip portions Y to vary the inclination thereof cyclically and collectively as the wing rotates;

a wing rotating tip jet unit mounted onone of said tip p t n r a further wing rotating jet unit mounted on said wing in diametrical opposition to said first jet unit;

a source of compressed gase's couplcd to said jet units; a and locking means to hold said Wing in a fixed position with said jet units disposed along the longitu dinal axis of the aircraft. V i 2. Ari aircraft comprising:

V J a winghav'nga center section and three radially ex- ,tending arms;

i said wing being mounted on saidairframe for rotation about an axis perpendicular to the plane of ,the wing at the center of symmetry thereof; 1

said arms havingtip portions comprising rotor elements pivotally mounted on substantially radial axes for inclination relativeto the chord plane of the wing; control means operatively connected to said tip portions 'to vary the inclination thereof cyclically and collectively as the wing rotates; a wing rotating tip jet unit mounted on one of said tip (portions; V a boom extending from said center section in diametrical opposition to said one tip portion; a further wing b V a source of compressed gases coupled to said jet units;

and locking means to hold said wing in a fixed posiis streamlined in' cross section in the direction of wing rotation;

.said boom having aflap longitudinally coextensive with V the trailing edge thereof;

said flap being substantially freely pivotalto vary the effective cross section of the boom in accordance lift of the boom. r

4. An aircraft according to claim 2, wherein said source of gases comprises:

a turbojet engine mounted in said airframe, said engine having an integral fan portion providing an annulus of cool air surrounding the primary exhaust gas flow: I

a distributor chamber connected to the exhaust on of said engine;

a. tailpipe extending rearwardly from said distributor chamber; a 'a rotor duct communicating from said distributor cham:

her to said jet units;

valve means to direct the engine exhaust flow selectively to said tailpipe and said rotor duct; and mixing inducing means in said distributor charns her to cause mixing of the combustion gases and cool air from said engine before entry into said rotor duct. 7 5. An aircraft according to claim 2, wherein said source of gases comprises: i

a turbojet engine mounted in said airframe, said engine having an integral fan portion providing an annulus of cool air surrounding the primary exhaust gas now; a

adistributor chamber connected to the exhaust end of said engine;

r a tailpipe extending rearwardly from saidrdistributor chamber; 1 I

:a rotor duct communicating from said distributor chamber to said jet units;-

'valve'm'eans to direct the: engine I tively to said tailpipe and said rotor duct; return ducts extending laterally and forwardly from said distributor chamberand having downwardly directed nozzles; V V V perforated mixingbafiles insaid distributor chamber to cause'mixing of the combustion gases and cool air from said engine before entry into said rotor.

duct; and a said mixing baffles communicating between said dis- 'tributing chamber and said return ducts.

6. An aircraft according-to claim ;2, wherein said source of gases comprises: I 7 i V a turbojet engine mounted in said airframe, said engine a distributor chamber connected of said engine;'

rotating jet unit. mounted on said exhaust flow seleca tailpipe extending rearwardly from said distributor chamber;

a rotor duct communicating from said distributor chamber to said jet units;

return ducts extending laterally and forwardly from said distributor chamber and having downwardly directed nozzles;

perforated mixing battles in said distributor chamber to cause mixing of the combustion gases and cool air from said engine before entry into said rotor duct;

said mixing battles communicating between said distributing chamber and said return ducts;

a rotor control valve mounted in said rotor duct;

outlet valves mounted in said return ducts;

said rotor control valve and said outlet valves being interconnected to move in unison between closed positions closing the respective ducts and open positions in the ducts;

and a thrust control valve mounted in said tailpipe and being coupled to said rotor control and outlet valves to move in opposition thereto between open and closed positions.

7. An aircraft comprising:

an airframe;

a wing having a center section and three radially extending arms;

said wing being mounted on said airframe for rotation about an axis perpendicular to the plane of the wing at the center of symmetry thereof;

said arms having tip portions comprising rotor elements pivotally mounted on substantially radial axes for inclination relative to the chord plane of the wing;

control means operatively connected to said tip portions to vary the inclination thereof cyclically and collectively as the wing rotates;

a wing rotating tip jet unit mounted on the tip portion of one of said arms;

a further Wing rotating jet unit mounted on said wing in diametrical opposition to said first jet unit;

a source of compressed gases coupled to said jet units;

drag brake elements mounted in the other two of said arms symmetrically relative to the axis through said jet units and being extensible into the surrounding airflow, whereby the resultant drag will stop rotation of the wing with said jet units disposed longitudinally to the direction of motion of the aircraft;

and locking means to secure said wing in fixed position with said jet units along the longitudinal axis of the aircraft.

References Cited by the Examiner UNITED STATES PATENTS 2,674,421 4/54 De Cenzo 244-71 3,025,022 3/62 Girard 244 7.1

FOREIGN PATENTS 827,852 2/60 Great Britain.

FERGUS S. MIDDLETON, Primary Examiner. 

1. AN AIRCRAFT COMPRISING: AN AIRFRAME; A WING HAVING A CENTER SECTION AND THREE RADIALLY EXTENDING ARMS; SAID WING BEING MOUNTED ON SAID AIRFRAME FOR ROTATION ABOUT AN AXIS PERPENDICULAR TO THE PLANE OF THE WING AT THE CENTER OF SYMMETRY THEREOF; SADI ARMS HAVING TIP PORTIONS COMPRISING ROTOR ELEMENTS PIVOTALLY MOUNTED ON SUBSTANTIALLY RADIAL AXES FOR INCLINATION RELATIVE TO THE CHORD PLANE OF THE WING; CONTROL MEANS OPERATIVELY CONNECTED TO SAID TIP PORTIONS TO VARY THE INCLINATION THEREOF CYCLICALLY AND COLLECTIVELY AS THE WING ROTATES; A WING ROTATING TIP JET UNIT MOUNTED ON ONE OF SAID TIP PORTIONS; A FURTHER WING ROTATING JET UNIT MOUNTED ON SAID WING IN DIAMETRICAL OPPOSITION TO SAID FIRST JET UNIT; A SOURCE OF COMPRESSED GASES COUPOLED TO SAID JET UNITS; AND LOCKING MEANS TO HOLD SAID WING IN A FIXED POSITION WITH SAID JET UNITS DISPOSED ALONG THE LONGITUDINAL AXIS OF THE AIRCRAFT. 